<html><head>
<title> FFA-W3-211, Free Transition </title></head>

<body BGPROPERTIES="FIXED" face="ARIAL" size="3" text="#000000"
bgcolor="#ffffff"  link="#ff0000" vlink="#aaaaff" alink="#FF00ff">

<br>
<center>
<H1>FFA-W3-211 AIRFOIL, Free Transition</H1>
</center>

<P><hr size=3 noshade></P>
<br>

Reynolds number = 1.8 x 10^6 <br><br>

Smooth airfoil (Free transition) <br><br>

Manufactured and equipped at FFA (The Aeronautical Research Institute
of Sweden) and measured at KTH, Royal Institute of
Technology, Stockholm (see
<A HREF="./../../HTML/biblio.htm#Bjorck">Bj&ouml;rck (1996)</A>) <br><br>

More details on computations and experimental facilities can be found in
the <A HREF="./../../HTML/report.htm"><font color="#006699">Wind Turbine
Airfoil Catalogue</font></A>.


<br><br><br>
<HR width=50% size=5>
<br><br>

<H1>DATA AVAILABLE:</H1><p><p>

- <A HREF="./../prof.dat"> Airfoil shape </A><p>

<font size=+3> Experiments:<br> </font>
- <A HREF="./cldm.exp"> Lift, Drag and Moment Coefficients </A><p>

<font size=+3> XFOIL Computations:<br> </font>
- <A HREF="./cldm.xf"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./cfp_08.0.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 08.0 deg. </A><br>
- <A HREF="./cfp_10.5.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 10.5 deg. </A><br>
- <A HREF="./cfp_13.0.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 13.0 deg. </A><br>
- <A HREF="./cfp_15.0.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 15.0 deg. </A><br>
- <A HREF="./cfp_17.0.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 17.0 deg. </A><br>
- <A HREF="./cfp_20.0.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 20.0 deg. </A><p>

<font size=+3> EllipSys2D Computations: </font><p>
<font size=+2><em>* With transition model:</em><br> </font>
- <A HREF="./cldm.ellipsys"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./cp_08.0.ellipsys"> Pressure Distribution - Angle of Attack = 08.0 deg. </A><br>
- <A HREF="./cp_10.5.ellipsys"> Pressure Distribution - Angle of Attack = 10.5 deg. </A><br>
- <A HREF="./cp_13.0.ellipsys"> Pressure Distribution - Angle of Attack = 13.0 deg. </A><br>
- <A HREF="./cp_15.0.ellipsys"> Pressure Distribution - Angle of Attack = 15.0 deg. </A><br>
- <A HREF="./cp_17.0.ellipsys"> Pressure Distribution - Angle of Attack = 17.0 deg. </A><br>
- <A HREF="./cp_20.0.ellipsys"> Pressure Distribution - Angle of Attack = 20.0 deg. </A><p>

- <A HREF="./cf_08.0.ellipsys"> Skin Friction Distribution - Angle of Attack = 08.0 deg. </A> <br>
- <A HREF="./cf_10.5.ellipsys"> Skin Friction Distribution - Angle of Attack = 10.5 deg. </A> <br>
- <A HREF="./cf_13.0.ellipsys"> Skin Friction Distribution - Angle of Attack = 13.0 deg. </A> <br>
- <A HREF="./cf_15.0.ellipsys"> Skin Friction Distribution - Angle of Attack = 15.0 deg. </A> <br>
- <A HREF="./cf_17.0.ellipsys"> Skin Friction Distribution - Angle of Attack = 17.0 deg. </A> <br>
- <A HREF="./cf_20.0.ellipsys"> Skin Friction Distribution - Angle of Attack = 20.0 deg. </A>


<br><br><br>
<HR width=50% size=5>
<br><br>

<H1>FIGURES AVAILABLE: (PostScript files)</H1><p><p>

- <A HREF="./../profile.ps"> Airfoil shape </A><p>

- <A HREF="./PS/cl.ps"> Lift Coefficient </A><br>
- <A HREF="./PS/cd.ps"> Drag Coefficient </A><br>
- <A HREF="./PS/cm.ps"> Moment Coefficient </A><p>

- <A HREF="./PS/cp_a08.0.ps"> Pressure Distribution - Angle of Attack = 08.0 deg. </A><br>
- <A HREF="./PS/cp_a10.5.ps"> Pressure Distribution - Angle of Attack = 10.5 deg. </A><br>
- <A HREF="./PS/cp_a13.0.ps"> Pressure Distribution - Angle of Attack = 13.0 deg. </A><br>
- <A HREF="./PS/cp_a15.0.ps"> Pressure Distribution - Angle of Attack = 15.0 deg. </A><br>
- <A HREF="./PS/cp_a17.0.ps"> Pressure Distribution - Angle of Attack = 17.0 deg. </A><br>
- <A HREF="./PS/cp_a20.0.ps"> Pressure Distribution - Angle of Attack = 20.0 deg. </A><p>

- <A HREF="./PS/cf_a08.0.ps"> Skin Friction Distribution - Angle of Attack = 08.0 deg. </A><br>
- <A HREF="./PS/cf_a10.5.ps"> Skin Friction Distribution - Angle of Attack = 10.5 deg. </A><br>
- <A HREF="./PS/cf_a13.0.ps"> Skin Friction Distribution - Angle of Attack = 13.0 deg. </A><br>
- <A HREF="./PS/cf_a15.0.ps"> Skin Friction Distribution - Angle of Attack = 15.0 deg. </A><br>
- <A HREF="./PS/cf_a17.0.ps"> Skin Friction Distribution - Angle of Attack = 17.0 deg. </A><br>
- <A HREF="./PS/cf_a20.0.ps"> Skin Friction Distribution - Angle of Attack = 20.0 deg. </A><p>



<br><br>
<HR width=50% size=5>
<br><br>

<TABLE border=0 width=100%>
<TR>
<TD align=left> <A HREF="./../../HTML/a_index.htm"><B><font color="#006699">
Back to airfoils index</font><B></A></TD>
<TD align=right><A HREF="./../../HTML/main.htm"><B><font color="#006699">
Back to airfoil catalogue home page</font></B></A></TD>
</TR>
</TABLE>
<br><br>

</BODY>
</html>
